[Federal Register Volume 71, Number 67 (Friday, April 7, 2006)]
[Unknown Section]
[Pages 17696-17698]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 06-3197]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23672; Directorate Identifier 2005-NM-237-AD; 
Amendment 39-14544; AD 2006-07-17]
RIN 2120-AA64


Airworthiness Directives; Boeing Model 727, 727C, 727-100, 727-
100C, and 727-200 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Boeing transport category airplanes. This AD requires 
determining if the terminal fittings of the spars of the wings are made 
of 7079 aluminum alloy material. For any positive finding, the AD 
requires doing repetitive inspections for cracks and corrosion of all 
exposed surfaces of the terminal fitting bores; doing repetitive 
inspections for cracks, corrosion, and other surface defects, of all 
exposed surfaces, including the flanges, of the terminal fitting; 
applying corrosion inhibiting compound to the terminal fittings; and 
repairing or replacing any cracked, corroded, or defective part with a 
new part. This AD also provides for an optional terminating action for 
the repetitive inspections. This AD results from reports of cracking of 
the terminal fittings of the spars of the wings. We are issuing this AD 
to detect and correct stress-corrosion cracking of the terminal 
fittings, which could result in the failure of one of the terminal 
fitting connections. Such a failure, combined with a similar failure of 
one of the other three terminal fittings, could result in the inability 
of the airplane structure to carry fail-safe loads, which could result 
in loss of structural integrity of the wing attachment points.

DATES: This AD becomes effective May 12, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of May 12, 2006.

ADDRESSES: You may examine the AD docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Daniel F. Kutz, Aerospace Engineer, 
Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
917-6456; fax (425) 917-6590.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at http://dms.dot.gov or in person at the Docket Management 
Facility office between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays. The Docket Management Facility office 
(telephone (800) 647-5227) is located on the plaza level of the Nassif 
Building at the street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to certain Boeing 
transport category airplanes. That NPRM was published in the Federal 
Register on January 25, 2006 (71 FR 4069). That NPRM proposed to 
require determining if the terminal fittings of the spars of the wings 
are made of 7079 aluminum alloy material. For any positive finding, the 
NPRM proposed to require doing repetitive inspections for cracks and 
corrosion of all exposed surfaces of the terminal fitting bores; doing 
repetitive inspections for cracks, corrosion, and other surface 
defects, of all exposed surfaces, including the flanges, of the 
terminal fitting; applying corrosion inhibiting compound to the 
terminal fittings; and repairing or replacing any cracked, corroded, or 
defective part with a new part. The NPRM also proposed to provide an 
optional terminating action for the repetitive inspections.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comment received. The 
commenter, Boeing, supports the NPRM.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Interim Action

    This AD is considered to be interim action. The inspection reports 
that are required by this AD will enable the manufacturer to obtain 
better insight into the extent of the cracking and corrosion of the 
terminal fittings of the front and rear spars of the wings in the 
fleet, and to develop additional action if necessary to address the 
unsafe condition. If additional action is identified, we may consider 
further rulemaking.

Costs of Compliance

    There are about 302 airplanes of the affected design in the 
worldwide fleet. This AD will affect about 157 airplanes of U.S. 
registry. The determination of forging number/material identification 
will take about 4 work hours per airplane, at an average labor rate of 
$65

[[Page 17697]]

per work hour. Based on these figures, the estimated cost of the AD for 
U.S. operators is $40,820, or $260 per airplane.
    Accomplishing the fluorescent dye penetrant and detailed 
inspections, if required, will take about 16 work hours per airplane, 
at an average labor rate of $65 per work hour. Based on these figures, 
we estimate the cost of the inspections to be $1,040 per airplane, per 
inspection cycle.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the National Government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2006-07-17 Boeing: Amendment 39-14544. Docket No. FAA-2006-23672; 
Directorate Identifier 2005-NM-237-AD.

Effective Date

    (a) This AD becomes effective May 12, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Boeing Model 727, 727C, 727-100, 727-
100C, and 727-200 series airplanes, certificated in any category; as 
identified in Boeing Alert Service Bulletin 727-57A0185, Revision 1, 
dated November 3, 2005.

Unsafe Condition

    (d) This AD results from reports of cracking of the terminal 
fittings of the front and rear spars of the wings. We are issuing 
this AD to detect and correct stress-corrosion cracking of the 
terminal fittings, which could result in the failure of one of the 
terminal fitting connections. Such a failure, combined with a 
similar failure of one of the other three terminal fittings, could 
result in the inability of the airplane structure to carry fail-safe 
loads, which could result in loss of structural integrity of the 
wing attachment points.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.
    Determination of Type of Terminal Fittings, Repetitive 
Inspections, and Corrective Actions
    (f) Within 24 months after the effective date of this AD, 
determine if the terminal fittings of the front and rear spars of 
the wings are made of 7079 aluminum alloy material by either 
inspecting the forging number or doing a conductivity test, in 
accordance with the Accomplishment Instructions of Boeing Alert 
Service Bulletin 727-57A0185, Revision 1, dated November 3, 2005.
    (1) If the forging number is that identified in Table 1 of this 
AD, or if the terminal fitting material is not made of 7079 aluminum 
alloy: No further action is required by this AD for that terminal 
fitting only.

Table 1.--Forging Numbers of Terminal Fittings Not Made of 7079 Aluminum
                                  Alloy
------------------------------------------------------------------------
   Forging number of  terminal fittings               Location
------------------------------------------------------------------------
(i) 65-16214-3............................  Rear spar of left wing.
(ii) 65-16213-3...........................  Front spar of left wing.
(iii) 65-16214-4..........................  Rear spar of right wing.
(iv) 65-16213-4...........................  Front spar of right wing.
------------------------------------------------------------------------

    (2) If any forging number other than those identified in Table 1 
of this AD is found, or if any forging material is made of 7079 
aluminum alloy, or if the material cannot be determined: Within 24 
months after the effective date of this AD, do the inspections 
specified in Table 2 of this AD and apply corrosion inhibiting 
compound (CIC) to the terminal fittings, and before further flight, 
repair or replace any cracked, corroded, or defective part found 
during the inspections. Repeat the inspections thereafter at 
intervals not to exceed 60 months for the first two repeat 
intervals, and then thereafter at intervals not to exceed 30 months. 
Do the inspections, application of CIC, and repair in accordance 
with the service bulletin, except as provided by paragraphs (h) and 
(i) of this AD. Do the replacement in accordance with paragraph (g) 
of this AD.

                          Table 2.--Inspections
------------------------------------------------------------------------
              Do--                       For--               Of--
------------------------------------------------------------------------
(i) A fluorescent dye penetrant   Cracks and          All exposed
 inspection.                       corrosion.          surfaces of the
                                                       terminal fitting
                                                       bores.
(ii) A detailed inspection......  Cracks, corrosion,  All exposed
                                   and other surface   surfaces,
                                   defects.            including the
                                                       flanges, of the
                                                       terminal fitting.
------------------------------------------------------------------------


[[Page 17698]]

Optional Terminating Action

    (g) Replacement of any terminal fitting of the front and rear 
spars of the wings with a new terminal fitting not made of 7079 
aluminum alloy, in accordance with a method approved by the Manager, 
Seattle Aircraft Certification Office (ACO), FAA, ends the 
repetitive inspections required by paragraph (f)(2) of this AD for 
that terminal fitting only. For the replacement to be approved by 
the Manager, Seattle ACO, as required by this paragraph, the 
Manager's approval letter must specifically refer to this AD.

Exception to Service Information

    (h) Where the service bulletin specifies to contact Boeing for 
appropriate action: Before further flight, repair the cracked, 
corroded, or defective part using a method approved in accordance 
with the procedures specified in paragraph (l) of this AD, or 
replace in accordance with paragraph (g) of this AD.
    (i) Although the note in paragraph 3.B.7. of the service 
bulletin specifies procedures for a fluorescent dye penetrant 
inspection of the body fitting bore and repair if necessary, those 
procedures are not required by this AD.

Parts Installation

    (j) As of the effective date of this AD, no person may install 
any terminal fitting having forging number 65-16213-1/-2 or 65-
16214-1/-2, or install any terminal fitting material made of 7079 
aluminum alloy, on any airplane.

Reporting

    (k) Submit a report of the findings (both positive and negative) 
of the initial inspection required by paragraph (f)(2) of this AD to 
Boeing Commercial Airplanes, Attention: Manager, Airline Support, 
P.O. Box 3707, Seattle, WA 98124-2207, at the applicable time 
specified in paragraph (k)(1) or (k)(2) of this AD. The report must 
include the operator's name, inspection results, a detailed 
description of any discrepancies found, the airplane serial number, 
and the number of flight cycles and flight hours on the airplane. 
Under the provisions of the Paperwork Reduction Act of 1980 (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements contained in this 
AD and has assigned OMB Control Number 2120-0056.
    (1) If the inspection was done after the effective date of this 
AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was accomplished prior to the effective 
date of this AD: Submit the report within 30 days after the 
effective date of this AD.

Alternative Methods of Compliance (AMOCs)

    (l)(1) The Manager, Seattle ACO, FAA, has the authority to 
approve AMOCs for this AD, if requested in accordance with the 
procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with Sec.  
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.
    (3) An AMOC that provides an acceptable level of safety may be 
used for any repair required by this AD, if it is approved by an 
Authorized Representative for the Boeing Commercial Airplanes 
Delegation Option Authorization Organization who has been authorized 
by the Manager, Seattle ACO, to make those findings. For a repair 
method to be approved, the repair must meet the certification basis 
of the airplane, and the approval must specifically refer to this 
AD.

Material Incorporated by Reference

    (m) You must use Boeing Alert Service Bulletin 727-57A0185, 
Revision 1, dated November 3, 2005, to perform the actions that are 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference of 
this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, 
Washington 98124-2207, for a copy of this service information. You 
may review copies at the Docket Management Facility, U.S. Department 
of Transportation, 400 Seventh Street SW., Room PL-401, Nassif 
Building, Washington, DC; on the Internet at http://dms.dot.gov; or 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at the NARA, call 
(202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on March 24, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-3197 Filed 4-6-06; 8:45 am]
BILLING CODE 4910-13-P